Sets forth a method of compliance with the requirements of Sections 23.903(b)(1), 25.901(d) and 25.903(d)(1) of the FAR pertaining to design precautions taken to minimize the hazards to an airplane in the event of uncontained engine or auxiliary power unit rotor (compressor and turbine) failure and engine fan blade failures. It is for guidance and to provide a method of compliance that has been found acceptable.

Alerts the aviation community to the potential hazards of water in aviation fuels. Additionally, it outlines recommended procedures to prevent, detect, and eliminate water in the fuel systems of aircraft.

Updates statistical information and brings to the attention of aircraft owners, operators, manufacturers, and maintenance personnel the circumstances surrounding engine power-loss accidents with recommendations on how those accidents can be prevented.

Provides information and guidance for use in evaluating and determining the eligibility of U.S. military surplus flight safety critical aircraft parts (FSCAP), engines, and propellers for installation on FAA type-certificated products.

Provides guidance regarding the inspection, maintenance, and installation of engine controls with emphasis on the airframe portion of these systems. It provides a supplement to, but does not replace, the procedures in the manufacturers’ maintenance manuals. Where the content of the AC differs from, or conflicts with the manufacturers’ maintenance manual, instructions contained in the manufacturers’ manual take precedence over the guidelines provide in this AC.

Provides guidance on the various aspects that should be considered in the FAA approval process of fire extinguishing system components manufactured under a Production Certificate (PC), components to be FAA approved under the Part Manufacturer Approval (PMA) process, or design changes to components originally approved by either method. This AC does not constitute a regulation, however, it provides a method, for obtaining approval of aircraft fire extinguishing system components. This is intended to enhance the standardization of all FAA Aircraft Certification Offices (ACO) and Manufacturing Inspection District Offices (MIDO) in the approval process of the critical components of an aircraft fire extinguishing system.

This advisory circular (AC) sets forth an acceptable means, but not the only means, for demonstrating compliance to the following by computer modeling analysis techniques validated by dynamic tests: • Title 14 Code of Federal Regulations (14 CFR) parts 23, 25, 27, and 29, §§ 23.562, 25.562, 27.562, and 29.562. • The Technical Standard Order (TSO) associated with the above regulations, TSO-C127/C127a.

This advisory circular (AC) provides guidance and acceptable methods, but not the only methods, for demonstrating compliance with the applicable engine induction system icing and engine ice ingestion requirements. These requirements are applicable to the Federal Aviation Regulations, parts 23, 25, and 33 of Title 14 of the Code of Federal Regulations (14 CFR parts 23, 25, and 33). The primary purpose of this AC is to reduce inconsistencies and eventual surprises to both engine manufacturers and engine installers, when installing a part 33 certified engine in a part 23 or 25 aircraft.

Provides general information and guidance concerning issuance of airworthiness certificates for U.S. registered aircraft, and issuance of special flight authorizations for operation in the United States of foreign aircraft not having standard airworthiness certificates issued by the country of registry.

Supplies one means for developers, integrators and applications to gain FAA acceptance of software.

This advisory circular (AC) provides recommended tire care and maintenance practices needed to assure the safety of support personnel and the continued airworthiness of aircraft. Specifically, this AC provides guidance on the installation, inflation, maintenance, and removal of aircraft tires. In addition, this AC provides guidance on those operational practices necessary to maintain safe aircraft operations. This AC is not mandatory and does not constitute a regulation. It is issued for guidance purposes and to outline acceptable tire maintenance and operational practices. In lieu of following this method without deviation, operators may elect to follow an alternative method that has also been found acceptable by the Federal Aviation Administration (FAA).

This advisory circular (AC) applies to manufacturers and installers of products or appliances incorporating complex custom micro-coded components with hardware design assurance levels of A, B, and C. These complex custom micro-coded components include application specific integrated circuits (ASIC), programmable logic devices (PLD), field programmable gate arrays (FPGA), or similar electronic components used in the design of aircraft systems and equipment. This AC provides a means (but not the only means) to gain Federal Aviation Administration (FAA) approval by showing the equipment design is appropriate for its intended function. Further, using this AC will help you satisfy airworthiness requirements when these types of electronic components are implemented

This advisory circular (AC) supports the introduction and the use of flight information Service Broadcast (FIS-B) weather and other aeronautical data link products for enhanced situational awareness. It identifies safety and interoperability requirements for continued airworthiness of aircraft FIS-B equipment, systems, and applications. Like all advisory material, this AC offers one way, but it is not the only way, to comply with regulations.

Provides information and suggested procedures to increase service life and to minimize blade failures of metal propellers.

Provides guidance and information for incorporation into operators' existing receiving/inspection systems to help prevent the introduction of unairworthy parts into inventories.

Provides a means of getting Federal Aviation Administration (FAA) approval of aircraft lightning protection.

Provides information and guidance concerning an acceptable means, but not the only means, of compliance with Parts 23 or 25 of the Federal Aviation Regulations (FAR) applicable to preventing ignition of fuel vapors due to lightning.

Provide a means to gain FAA approval of you aviation databus by showing the databus design performs it intended function and satisfies the applicable airworthiness requirements when install on an aircraft or aircraft engine

Provides information relating to the substantiation of ice protection systems on aircraft.

This AC shows you how to develop and use a reliability assessment plan. An assessment plan documents the controlled, repeatable processes for assessing the reliability of aircraft and engine electronic and electrical systems, including their electromechanical elements and equipment

Informs owners and operators about the usefulness of manufacturers’ maintenance manuals for servicing, repairing, and maintaining aircraft, engines and propellers.

This AC will guide you in obtaining a design and production approval inder Technical Standard Order (TSO) C-165, Electronic Map Display Equipment for Graphical Depiction of Aircraft Position, for the software used to provide an airport moving map display(AMMD) intended for use on a Class 2 electronic flight bag (EFB).

This advisory circular (AC) will show you how to gain Federal Aviation Administration (FAA) approval of your compliance with Title 14, Code of Federal Regulations (14 CFR) §§ 23.1308, 25.1317, 27.1317, and 29.1317, High-intensity Radiated Fields (HIRF) protection. This AC is not mandatory and does not constitute a regulation. It describes an acceptable means, but is not the only means, to show you how to gain certification for protection of the operation of electrical and electronic systems on an aircraft when the aircraft is exposed to an external HIRF environment. However, if you use the means described in this AC, you must follow it in all important respects.

The AC offers one way to achieve an acceptable level of performance for an aircraft recording system when a controller-pilot data communication capability is installed. We wrote this AC for aircraft equipment installers and type certificate applicants to identify design approval requirements for data link communication recording equipment.